| Project/Area Number |
18360412
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
ONODA Junjiro Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Department of Space structure and Materials, Professor (20013740)
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| Co-Investigator(Kenkyū-buntansha) |
MINESUGI Kenji Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Department of Space structure and Materials, Associate Professor (90239327)
SHIMOSE Shigeru Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Center of Space Science Technology, Chief Engineer (80443282)
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| Project Period (FY) |
2006 – 2007
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| Project Status |
Completed (Fiscal Year 2007)
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| Budget Amount *help |
¥9,070,000 (Direct Cost: ¥8,200,000、Indirect Cost: ¥870,000)
Fiscal Year 2007: ¥3,770,000 (Direct Cost: ¥2,900,000、Indirect Cost: ¥870,000)
Fiscal Year 2006: ¥5,300,000 (Direct Cost: ¥5,300,000)
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| Keywords | Satellite / Vibration Suppression / Energy-Recycling / Semi-Active Vibration Suppression |
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| Research Abstract |
This study is the first step for the application of the energy-recycling semi-active vibration suppression method to an actual satellite. A model used in the study is an actual structural test model (STM) of the interplanetary probe “SUISEI". Lots of vibration suppression experiments were conducted on the STM in order to confirm a control efficiency of the method. A finite element model of the STM was made and modal analysis was executed by using the model, A controlled vibration mode was determined according to the result of the analysis and was identified by the experiment. Eighty-one piezoelectric materials were bonded on the STM based on the modal deformation of the controlled mode. A system employing the energy-recycling semi-active vibration suppression method was established with these piezoelectric materials and vibration suppression experiments were executed by exciting vibration on the STM by a small shaker and a large shaker. The results of the analysis and experiments are a
… More
s follows.
1. The method worked effectively on the vibration suppression of the STM of an actual satellite by the system that consists of actual piezoelectric materials and available electrical parts.
2. The method showed the higher performance than a traditional semi-active method that only dissipated energy transformed by piezoelectric materials.
3. The method worked well on the vibration suppression of both a global mode and a local mode of the STM. Especially, it showed good performance in case of the local mode.
4. The method worked well on the vibration suppression not only in case of sinusoidal excitation but also in case of random excitation, which was close to an actual vibration environment in a powered flight phase. The control efficiency in case of the random excitation was investigated
5. The relation of a connection of piezoelectric materials to the control efficiency was investigated and it was confirmed analytically and experimentally that the method showed better performance in case of a series connection rather than in case of parallel connection.
6. Completely non power supply energy-recycling semi-active vibration suppression method was applied to the STM model and it was confirmed that the system employing the method worked correctly.
The study showed useful results for the practical application of the energy-recycling semi-active vibration suppression method to an actual satellite. These results are expected to contribute to a solution of vibration problems not only in the aerospace field but also in lots of fields. Less
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